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| Number | Title | Issue Date |
| 7281683 | Process for aiding the takeoff of an aircraft An aircraft takeoff process may include applying a pitch command deflecting an adjustable horizontal tailplane of the aircraft by a predetermined angle. Thereafter, the pitch command is corrected in accordance with the deviation between a takeoff rotation speed and ... | 10/16/2007 |
| 7031811 | Fuel efficient airspeed trim A system and method are provided for precisely adjusting individual aircraft airspeed system in order to provide more accurate cruise Indicated Airspeed (IAS). The system includes a flight data computer, an autopilot, and airspeed displays. The flight data computer ... | 04/18/2006 |
| 7007897 | Flight control actuation system A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level ... | 03/07/2006 |
| 6942057 | Feel control for active steering A method and apparatus for controlling the feel back torque of a motor provides for receiving a difference between a desired motor position and an actual motor position; filtering the difference into two or more frequency bands; and applying a gain to one or more of... | 09/13/2005 |
| 6827311 | Flight control actuation system A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level ... | 12/07/2004 |
| 6772054 | Device for operating a controlled member on a rotary-wing aircraft, particularly a helicopter An apparatus for operating a controlled member on a rotary-wing aircraft is provided with at least one control intended to be subject to the action of a pilot of the rotary-wing aircraft and capable of moving a linkage, a device connected to the linkage for operatin... | 08/03/2004 |
| 6675076 | System, autopilot supplement assembly and method for increasing autopilot control authority A system is provided for increasing autopilot control authority in a vehicle, such as aircraft including mechanical control systems. The system includes an autopilot system, a control element and an autopilot supplement assembly. The autopilot system can ... | 01/06/2004 |
| 6505115 | Device for controlling a system for monitoring the environment of an aircraft, in particular of a transport aircraft The control device (1) comprises at least one first and one second control system (4, 5) which comprises control elements (A1 to A8, B1 to B6) actuable by an operator, so as to control the monitoring system (2). These first and second control systems (4, ... | 01/07/2003 |
| 6325333 | Aircraft pitch-axis stability and command augmentation system A bias correction system for use in a neutrally-stable aircraft having a control column and a pitch control system is provided. The position of the control column is generally represented by a control column position signal. The bias correction system is ... | 12/04/2001 |
| 6241182 | Hybrid control system for an aircraft aerodynamic surface System for controlling an aerodynamic surface (1) (flap, aileron, control surface, etc.) of an aircraft. According to the invention, this system comprises: an electric machine (8) which can operate either as a motor or as a generator, the output of which is co... | 06/05/2001 |
| 6206329 | Process and device for the control of the rudder of an aircraft A device for the control of a control surface of an aircraft has at least two actuators (110, 112, 114), each having at least one electric control input (111a, 113a, 115a). At least one of the actuators (115), called the mixed actuator, also has a mechani... | 03/27/2001 |
| 5908177 | Flight control system Herein disclosed is a flight control system comprising a control member, a control surface controllable to assume different angle positions within a control angle range, a transmission linkage provided between the control member and the control surface to... | 06/01/1999 |
| 5806805 | Fault tolerant actuation system for flight control actuators A fault tolerant actuation system (12) for flight control systems is provided. The fault tolerant actuation system (12) includes a plurality of primary flight computers (14a, 14b, and 14c) with corresponding power control units (24a, 24b, and 24c). Each p... | 09/15/1998 |
| 5791596 | Process and device for the control of the rudder of an aircraft A device for controlling a rudder of an aircraft has at least two servo-systems each including at least one electric control input. At least one of the servo-systems is a mixed servo-system that also has a mechanical control input. When an engine fault oc... | 08/11/1998 |
| 5374014 | System for control of an aerodynamic surface of an aircraft System for control of an aerodynamic surface (1) of an aircraft, comprising an intentional actuation member (5) and a hydraulic jack (2) intended to deflect said aerodynamic surface (1). According to the invention, the system comprises means (14) for detecting... | 12/20/1994 |
| 5319296 | Oscillatory servo-valve monitor An oscillatory servo-valve fault monitor is provided for identifying faults attributable to servo-control system components. In particular, both low frequency and high frequency (oscillatory) fault responses are identified. Such oscillatory fault response... | 06/07/1994 |
| 5109672 | Method and apparatus for cooling and replenishing aircraft hydraulic actuators A system for cooling individual integrated actuator packages (IAPs) positioned throughout the aircraft in a power-by-wire actuation system is disclosed. A low-pressure hydraulic fluid circulates throughout the aircraft to control the temperature of the in... | 05/05/1992 |
| 5082208 | System and method for controlling an aircraft flight control member A control system and method for controlling a flight control member employs a hydraulic control valve which is responsive to input from the pilot in a manner to start and stop a hydraulic motor which in turn starts and stops movement of the control member... | 01/21/1992 |
| 5033694 | Attitude control device for air or sea transportation craft An attitude control system for controlling a plurality of attitude control devices, which cooperate to establish the attitude of a vehicle includes redundant control units for outputting attitude control signals to each of the attitude control devices. Ad... | 07/23/1991 |
| 4863337 | Control system for working machine having boom A control system for a working machine which has a boom equipped with a working implement at its forward end and pivoted to a vehicle body movably about a vertical axis, and control valve for controlling the movement of the boom. The system comprises a va... | 09/05/1989 |
| 4800798 | Control surface dual redundant servomechanism A dual redundant servomechanism for moving aircraft control surfaces is disclosed. The servomechanism is of the type whose input commands, from the pilot of the aircraft, are transmitted electrically. Force fight, which is associated with such dual servom... | 01/31/1989 |
| 4762294 | Elevator control system especially for an aircraft An elevator control system especially for an aircraft such as an airplane, s equipped with an electrically controllable elevator flap drive system for the elevator flap on each side of the aircraft. Additionally, the system is equipped with a mechanically ... | 08/09/1988 |
| 4759515 | Drive control for a vertical rudder of an aircraft A vertical rudder control and drive system for an aircraft, such as an aiane, is equipped with electrically controllable vertical rudder drive systems on each side of the aircraft. Additionally, the control system is equipped with a mechanically controll... | 07/26/1988 |
| 4667472 | Electric integrated actuator with variable gain hydraulic output This invention relates to integrated electro-hydraulic actuators for use aboard aircraft or elsewhere. A balanced, double-acting hydraulic ram or motor (12) is connected between a support (16) and a member to be moved relative to the support. The ram incl... | 05/26/1987 |
| 4580210 | Control system having variably biased manipulatable unit In a control system having a manipulatable unit, such as an aircraft stick, which is biased toward a neutral position to provide control "feel", an input which at each instant signifies the position of displacement of the stick from its neutral position i... | 04/01/1986 |
| 4403756 | Bifurcated feel simulator for aircraft A bifurcated feel unit for use in a dual path flight control system includes separate input levers for the pilot and copilot control paths. The input levers pivot about a common axis but are capable of independent rotation upon override of the breakout po... | 09/13/1983 |
| 4313165 | Force feel actuator with limited proportional/integral error feedback A system which provides feel-force to the control stick of an aircraft by means of hydraulic pressure is provided with non-nulling, proportional, direct feedback loop, and a limited integral feedback loop in the drive of the pressure control servo valve t... | 01/26/1982 |
| 4150803 | Two axes controller A two axis controller for controlling a tanker aircraft in-flight refueling boom while maneuvering prior to engagement with the receiver aircraft and including a boom load alleviation system after engagement. Movement of the control stick is transmitted m... | 04/24/1979 |
| 3960348 | Aerodynamic surface control feel augmentation system In a helicopter, a pilot-actuated lever controls, through linkage mechanisms, a servo valve to drive a hydraulic piston; the piston moves a swash plate which in turn controls movement of rotor blade pitch positioning mechanisms against the force of blade ... | 06/01/1976 |
| 3949958 | Pitch control system An improved system of pitch control for aircraft having a "flying tail"; i.e., a movable horizontal stabilizer with at least one movable elevator thereon. The human or automatic pilot input commands operate the elevators, and then the elevator response is... | 04/13/1976 |
